Abstract: The working environment of the four-directional carbon/carbon(C/C)composites for throat in solid rocket motor is confronted with high-temperature， high-pressure， high-speed， ablation and erosion of a large amount of gas-particle two-phase flow， which is very strict on the ablation resistance and thermal structural characteristics of the 4D C/C composites. Therefore， based on experiment of ablation and thermal structure characteristic， thermal structure properties prediction and simulation of gas-particle two-phase flow， the research progress of ablation and thermal structure characteristic of the 4D C/C composites is discussed. This paper gives that the control of the ablation parameters and simulating real ablation working environment are the difficulties of ablation experiment. The working condition under the addition of aluminum particles and measurement experiment of thermal structure properties based on mesoscale are the emphasises in experiment. It is proposed to conduct ablation experiments from the type of specimen， the design of the experimental program， and the comparison aluminum particles for two conditions. The thermal stability material was used to replace the interface in the experiment of thermal structural characteristic. The influence of the interface between the component materials on the thermal structure properties prediction based on mesoscale is the difficulty to simulate. The representative volume element on the basis of the periodic boundary conditions of temperature to predict the thermal structure properties is proposed. In the simulation of gas-particle two-phase flow， the coupling of different phases in the engine and the erosion mechanical of the 4D C/C composites are difficulties in numerical simulation. The SDPH-FVM coupling method is proposed to solve the flow field. The problem of combustion flow can be further used to reveal the combustion mechanism of the flow field.

Key words: Four-directional carbon/carbon composites；Ablation experiment；Representative volume element；Periodic boundary conditions of temperature；Gas-particle two-phase flow；Mesoscale

摘要： 固体火箭发动机喉衬用轴编C/C复合材料的工作环境面临高温、高压、高速燃气流和大量凝聚相颗粒的烧蚀和冲刷，对材料的抗烧蚀性能和热结构特性要求十分严格。因此，从烧蚀实验和热结构特性实验研究、热结构特性预测与气体-颗粒两相流数值模拟三个方面，论述了轴编C/C复合材料的烧蚀及热结构特性研究进展。总结讨论了实现真实烧蚀工作环境的模拟和影响烧蚀实验参数的控制是高温烧蚀实验的难点，对于铝颗粒添加下工况的烧蚀实验和在细观尺度下热结构特性参数的测定实验是重点；提出从实验件类型、实验系统设计和对比有无铝颗粒添加下的工况进行烧蚀实验；提出采用一种热稳定性材料取代界面的实验方案进行热结构特性参数的测定实验。在热结构特性研究的细观尺度方面，组分材料之间的界面对热结构特性的影响有待深入研究，提出在代表性体积单元模型的基础上引入温度的周期性边界条件来实现热结构参数的预测。在气粒两相流数值模拟方面，发动机内不同相之间相互耦合作用以及对轴编C/C复合材料的机械侵蚀是数值模拟研究的难点，提出使用SDPH-FVM耦合的方法去解决内流场燃烧流动的问题，进一步可用来揭示内流场燃烧流动机理。

关键词: 轴编C/C复合材料；烧蚀实验；代表性体积单元；温度周期性边界条件；气体-颗粒两相流；细观尺度